NDLI: LIF imaging of species and temperature in technical combustion at elevated pressures

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Table of contents

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Experimental investigations on vortex breakdown over delta wings with Doppler global velocimetry

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Measurement technology of the impact of alumina liquid particles on a hot surface

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Vortical flow field investigation using a two-component pressure sensitive paint at low speed

Implementing pressure-sensitive paint in the AFRL subsonic aerodynamic research laboratory

Pressure-sensitive-paint measurements in a large-scale commercial-engine test stand

Pressure sensitive paint measurements on a wing model in a low-speed wind tunnel

Application of the direct PSP-lifetime method on pyren-based paint as a completion of the existing DLR PSP system

Pressure sensitive paint for oscillating pressure fields measurements

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Development and applications of a rapid flight test prototyping system for unmanned air vehicles

An optical technique for detecting fatigue cracks in aerospace structures

Investigations on a dynamic forebody flow control system

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A new approach to measuring model deflection

Feasibility of airfoil tests with a small high subsonic cryogenic wind tunnel

Determination of residual wall interferences for measurements on the TWIG model-comparison of different methods and analysis

Electronically scanned pressure measurement scanner for cryogenic wind tunnel applications

Using of oscillatory conning experimental rig for separation of rotary and unsteady aerodynamic derivatives

Determining the transfer function for unsteady pressure measurements using a method of characteristics solution

A re-evaluation of a pulsed laser technique for measuring surface heat transfer coefficients

Performance studies of the constant voltage anemometer in a Mach 2.3 boundary layer

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LIF imaging of species and temperature in technical combustion at elevated pressures

Content Provider	IEEE Xplore Digital Library
Author	Meier, U.E. Wolff-Gassmann, D. Heinze, J. Frodermann, M. Magnusson, I. Josefsson, G.
Copyright Year	1999
Description	Author affiliation: Inst. of Combustion Technol., German Aerosp. Center, Germany (Meier, U.E.)
Abstract	Planar laser-induced fluorescence (PLIF) has been used to measure time-resolved spatial distributions of temperature, fuel and OH in an SI engine, modified for optical access, and a jet engine combustion chamber segment. For temperature measurements, a two-line PLIF scheme was used: Two different rotational lines of the OH radical, which served as indicator molecule, were excited successively using nanosecond pulses from two laser systems operating on different wavelengths. The resulting fluorescence intensity is proportional to the population of the initial rotational state; the ratio of the two fluorescence signals is therefore proportional to the ratio of the populations, which in turn depends on the temperature. The fluorescence signal resulting from excitation by one of the two lasers is proportional to the OH density and provides thus information on flame structure. If the laser is tuned away from an OH resonance, fluorescence resulting from kerosene can be observed. The measurements presented here provide information on flame structure, heat release and mixing properties, which can serve as design aids, as well as for CFD code validation purposes.
File Size	904618
File Format	PDF
ISBN	0780357159
DOI	10.1109/ICIASF.1999.827146
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	1999-06-14
Publisher Place	France
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Combustion Fluorescence Laser excitation Laser tuning Fires Optical imaging Temperature distribution Fuels Engines Optical mixing
Content Type	Text
Resource Type	Article

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